AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 500,000 Max Cl/Cd: 113.25 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k136-il-500000.txt Download as CSV file: xf-ah88k136-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-136/16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2158 0.10132 0.09865 -0.0690 0.8059 0.0255
-11.500 -0.2206 0.09620 0.09354 -0.0719 0.8052 0.0258
-11.250 -0.2224 0.09158 0.08894 -0.0740 0.8045 0.0259
-11.000 -0.2259 0.08663 0.08400 -0.0762 0.8036 0.0260
-10.750 -0.2351 0.08087 0.07827 -0.0772 0.8027 0.0266
-10.500 -0.2349 0.07737 0.07478 -0.0781 0.8017 0.0269
-10.250 -0.2351 0.07387 0.07129 -0.0791 0.8009 0.0272
-10.000 -0.4508 0.04938 0.04630 -0.0952 0.8018 0.0165
-9.750 -0.4634 0.04772 0.04456 -0.0911 0.8002 0.0167
-9.500 -0.4887 0.04501 0.04166 -0.0847 0.7989 0.0167
-9.250 -0.5224 0.03942 0.03561 -0.0771 0.7978 0.0158
-9.000 -0.5340 0.03640 0.03220 -0.0718 0.7968 0.0159
-8.750 -0.5400 0.03302 0.02847 -0.0674 0.7943 0.0158
-8.500 -0.5387 0.03034 0.02537 -0.0635 0.7921 0.0159
-8.250 -0.5337 0.02773 0.02232 -0.0600 0.7905 0.0163
-8.000 -0.5214 0.02554 0.01988 -0.0578 0.7892 0.0168
-7.750 -0.5025 0.02487 0.01914 -0.0566 0.7881 0.0175
-7.500 -0.4829 0.02405 0.01818 -0.0553 0.7871 0.0182
-7.250 -0.4623 0.02311 0.01706 -0.0541 0.7862 0.0189
-7.000 -0.4405 0.02240 0.01617 -0.0530 0.7854 0.0199
-6.750 -0.4183 0.02150 0.01507 -0.0520 0.7847 0.0208
-6.500 -0.3964 0.02067 0.01422 -0.0513 0.7834 0.0222
-6.250 -0.3729 0.02039 0.01393 -0.0510 0.7808 0.0237
-6.000 -0.3490 0.01993 0.01340 -0.0505 0.7789 0.0250
-5.750 -0.3253 0.01934 0.01271 -0.0499 0.7772 0.0263
-5.500 -0.3031 0.01866 0.01203 -0.0491 0.7757 0.0285
-5.250 -0.2794 0.01839 0.01172 -0.0484 0.7745 0.0308
-5.000 -0.2554 0.01814 0.01140 -0.0477 0.7735 0.0326
-4.750 -0.2347 0.01743 0.01068 -0.0464 0.7726 0.0359
-4.500 -0.2107 0.01721 0.01043 -0.0457 0.7718 0.0395
-4.250 -0.1887 0.01681 0.00999 -0.0446 0.7711 0.0440
-3.750 -0.1450 0.01658 0.00981 -0.0431 0.7651 0.0552
-3.500 -0.1213 0.01644 0.00966 -0.0425 0.7631 0.0627
-3.250 -0.0987 0.01615 0.00941 -0.0415 0.7615 0.0731
-3.000 -0.0751 0.01589 0.00919 -0.0408 0.7603 0.0866
-2.750 -0.0512 0.01562 0.00896 -0.0400 0.7592 0.1058
-2.500 -0.0279 0.01529 0.00874 -0.0392 0.7584 0.1386
-2.250 -0.0060 0.01486 0.00852 -0.0381 0.7575 0.1956
-2.000 0.0079 0.01439 0.00855 -0.0359 0.7544 0.3256
-1.750 0.0064 0.01353 0.00858 -0.0307 0.7495 0.5586
-1.500 0.0509 0.01289 0.00913 -0.0334 0.7486 0.8807
-1.250 0.0732 0.01316 0.00935 -0.0316 0.7471 0.9043
-1.000 0.1120 0.01346 0.00958 -0.0334 0.7462 0.9172
-0.750 0.1576 0.01381 0.00986 -0.0365 0.7456 0.9290
-0.500 0.2491 0.01431 0.01028 -0.0494 0.7457 0.9334
-0.250 0.2862 0.01446 0.01038 -0.0509 0.7448 0.9436
0.000 0.3606 0.01450 0.01035 -0.0604 0.7446 0.9473
0.250 0.4113 0.01450 0.01030 -0.0649 0.7441 0.9552
0.500 0.4459 0.01425 0.01001 -0.0663 0.7434 0.9594
0.750 0.4843 0.01392 0.00964 -0.0686 0.7428 0.9610
1.000 0.5165 0.01412 0.00990 -0.0703 0.7367 0.9637
1.250 0.5486 0.01391 0.00969 -0.0714 0.7346 0.9668
1.500 0.5719 0.01376 0.00951 -0.0704 0.7330 0.9716
1.750 0.6101 0.01327 0.00902 -0.0727 0.7318 0.9728
2.000 0.6469 0.01284 0.00858 -0.0747 0.7307 0.9743
2.250 0.6823 0.01241 0.00813 -0.0764 0.7296 0.9761
2.500 0.7162 0.01202 0.00773 -0.0778 0.7284 0.9781
2.750 0.7416 0.01213 0.00793 -0.0778 0.7222 0.9814
3.000 0.7711 0.01185 0.00767 -0.0782 0.7192 0.9840
3.250 0.8072 0.01135 0.00718 -0.0801 0.7168 0.9853
3.500 0.8428 0.01085 0.00667 -0.0818 0.7144 0.9867
3.750 0.8729 0.01075 0.00666 -0.0827 0.7078 0.9887
4.000 0.9044 0.01041 0.00634 -0.0836 0.7028 0.9906
4.250 0.9349 0.01015 0.00611 -0.0843 0.6984 0.9924
4.500 0.9631 0.01004 0.00608 -0.0847 0.6894 0.9943
4.750 0.9955 0.00973 0.00582 -0.0859 0.6783 0.9957
5.000 1.0261 0.00937 0.00540 -0.0866 0.6552 0.9973
5.250 1.0521 0.00929 0.00519 -0.0864 0.6155 0.9989
5.500 1.0707 0.00961 0.00522 -0.0848 0.5578 1.0000
5.750 1.0789 0.01033 0.00564 -0.0813 0.5006 1.0000
6.000 1.0887 0.01104 0.00614 -0.0784 0.4548 1.0000
6.500 1.1024 0.01274 0.00739 -0.0718 0.3591 1.0000
6.750 1.1050 0.01372 0.00813 -0.0680 0.3113 1.0000
7.000 1.1046 0.01471 0.00891 -0.0636 0.2690 1.0000
7.250 1.0964 0.01578 0.00979 -0.0580 0.2269 1.0000
7.500 1.0744 0.01670 0.01059 -0.0497 0.2019 1.0000
7.750 1.0564 0.01776 0.01151 -0.0426 0.1731 1.0000
8.000 1.0393 0.01902 0.01251 -0.0359 0.1299 1.0000
8.250 1.0241 0.02038 0.01357 -0.0297 0.0822 1.0000
8.500 1.0098 0.02184 0.01474 -0.0238 0.0421 1.0000
8.750 1.0106 0.02270 0.01558 -0.0200 0.0333 1.0000
9.000 1.0090 0.02372 0.01658 -0.0160 0.0277 1.0000
9.250 1.0149 0.02438 0.01730 -0.0131 0.0255 1.0000
9.500 1.0181 0.02520 0.01815 -0.0098 0.0235 1.0000
9.750 1.0157 0.02634 0.01933 -0.0060 0.0217 1.0000
10.000 1.0196 0.02714 0.02021 -0.0030 0.0209 1.0000
10.250 1.0232 0.02799 0.02111 0.0001 0.0197 1.0000
10.500 1.0267 0.02885 0.02201 0.0030 0.0186 1.0000
10.750 1.0281 0.02990 0.02308 0.0061 0.0178 1.0000
11.000 1.0246 0.03135 0.02458 0.0094 0.0170 1.0000
11.250 1.0258 0.03269 0.02599 0.0121 0.0162 1.0000
11.500 1.0312 0.03392 0.02729 0.0142 0.0159 1.0000
11.750 1.0374 0.03519 0.02864 0.0160 0.0154 1.0000
12.000 1.0428 0.03662 0.03013 0.0177 0.0149 1.0000
12.250 1.0495 0.03801 0.03157 0.0192 0.0143 1.0000
12.500 1.0557 0.03950 0.03310 0.0207 0.0138 1.0000
12.750 1.0607 0.04113 0.03475 0.0221 0.0132 1.0000
13.000 1.0645 0.04292 0.03661 0.0238 0.0125 1.0000
13.250 1.0738 0.04430 0.03809 0.0247 0.0122 1.0000
13.500 1.0821 0.04582 0.03970 0.0260 0.0120 1.0000
13.750 1.0903 0.04736 0.04134 0.0269 0.0115 1.0000
14.000 1.0980 0.04900 0.04307 0.0279 0.0111 1.0000
14.250 1.1056 0.05070 0.04485 0.0290 0.0108 1.0000
14.500 1.1136 0.05239 0.04665 0.0298 0.0108 1.0000
14.750 1.1180 0.05439 0.04870 0.0303 0.0103 1.0000
15.000 1.1239 0.05637 0.05076 0.0312 0.0101 1.0000
15.250 1.1296 0.05842 0.05288 0.0321 0.0098 1.0000
15.500 1.1331 0.06080 0.05544 0.0328 0.0100 1.0000
16.250 1.1193 0.07152 0.06675 0.0349 0.0095 1.0000
16.500 1.1097 0.07575 0.07118 0.0348 0.0095 1.0000
16.750 1.0962 0.08044 0.07609 0.0336 0.0093 1.0000
17.000 1.0856 0.08532 0.08112 0.0337 0.0095 1.0000
17.500 1.0555 0.09641 0.09259 0.0298 0.0094 1.0000
17.750 0.8365 0.15098 0.14862 0.0049 0.0199 1.0000
18.000 0.5854 0.15228 0.15012 0.0084 0.0238 1.0000
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